EP3627013A1 - Low friction carbon - carbon seal assembly - Google Patents
Low friction carbon - carbon seal assembly Download PDFInfo
- Publication number
- EP3627013A1 EP3627013A1 EP19198453.3A EP19198453A EP3627013A1 EP 3627013 A1 EP3627013 A1 EP 3627013A1 EP 19198453 A EP19198453 A EP 19198453A EP 3627013 A1 EP3627013 A1 EP 3627013A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- seal
- carbon
- seat
- seal assembly
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- CREMABGTGYGIQB-UHFFFAOYSA-N carbon carbon Chemical compound C.C CREMABGTGYGIQB-UHFFFAOYSA-N 0.000 title description 4
- 239000011203 carbon fibre reinforced carbon Substances 0.000 title description 4
- 238000007789 sealing Methods 0.000 claims abstract description 23
- 239000003575 carbonaceous material Substances 0.000 claims abstract description 15
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 33
- 229910052799 carbon Inorganic materials 0.000 claims description 33
- 239000000463 material Substances 0.000 claims description 11
- 229910002804 graphite Inorganic materials 0.000 claims description 3
- 239000010439 graphite Substances 0.000 claims description 3
- 239000010408 film Substances 0.000 description 16
- 238000010438 heat treatment Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/3404—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member and characterised by parts or details relating to lubrication, cooling or venting of the seal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/3496—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member use of special materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/224—Carbon, e.g. graphite
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
Definitions
- the disclosure relates to a seal assembly, and more particularly to a bearing seal for a gas turbine engine.
- Gas turbine engines have rotating elements mounted within stationary components at bearings which must be sealed to prevent escape of oil.
- Such seals are known as bearing seals or oil seals.
- One form of seal for such purpose is a carbon seal, where a carbon material seal is closely positioned around or relative to a rotating element. When first operated, such a seal results in the transfer of carbon from the carbon seal to the rotating element or seat of the seal assembly to form a film of carbon on the seat. This film is intended to have a low coefficient of friction with the seal, such that escape of oil between the seal and seat is prevented while operating at an acceptably low coefficient of friction.
- break-in phase of the seal This period of operation, when the film is formed, is referred to as the break-in phase of the seal.
- break-in excessive friction can be created, resulting in potential excessive wear on parts of the seal, excessive heat at locations of the seal or seat, and other issues.
- This issue is all the more serious in seals which are to operate at high velocity and relatively low pressure, which can increase the already high temperature due to friction. The present disclosure addresses this issue.
- a seal assembly for a gas turbine engine comprising a seal comprising a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the seal and the seal seat each have a sealing surface which together define a sliding seal, and wherein at least the sealing surface of the seal seat is made of the same carbon material as the sealing surface of the seal.
- the seal seat has a recessed area, and a carbon-based block mounted in the recess, the carbon-based block defining the sealing surface of the seal seat.
- the seal seat itself comprises carbon-based material matching the seal.
- the sealing surfaces of the seal and the seal seat are the same material selected from the group consisting of electrographitic grade carbon, carbon-graphite grade carbon, and combinations thereof.
- the sealing surfaces of the seal and the seal seat define a coefficient of friction of less than 0.1.
- the disclosure relates to a seal assembly for a gas turbine engine and, more particularly, to a carbon seal assembly for the oil seals of a gas turbine engine.
- FIG. 1 is a cross-sectional illustration of a portion of a gas turbine engine, and illustrates typical components of such an engine.
- a rotational shaft 10 to which are coupled various operative components of the engine, and stationary structures 12, 14, 16, 18 which cooperate with structure 10 to perform desired functions.
- Other features of the engine have been removed from the view of FIG. 1 , or reduced to simple schematic illustration, to allow focus on features which are pertinent to the present disclosure.
- FIG. 1 illustrates a front seal assembly 20 and a rear seal assembly 22, each of which serves to prevent leakage or flow of oil past the seal, and thereby maintain oil where desired and needed in the gas turbine engine.
- Seal assembly 20 is defined by a front seal seat 24 and a carbon seal 26. Carbon seal 26 remains stationary relative to rotating element 10 and seal seat 24. As shown in FIG. 1 , each of these components has a sealing surface 28, 30, which together define the seal. These surfaces 28, 30 slide relative to each other and prevent leakage of oil through these surfaces.
- seal assembly 22 is defined by a rear seal seat 32 and a carbon seal 34, each of which defines sealing surfaces 36, 38 to prevent leakage of oil through these surfaces.
- FIG. 2 illustrates portions of a carbon seal 34 and seal seat 32, including surfaces 36, 38.
- Seal seat 32 in this known configuration is typically formed of a material such as an Fe-based alloy such as AMS 6490/6491, AMS 6322, or AMS 6323, which may or may not have an additional material applied to it such as a PWA50 material.
- the material of the seal seat starts with a relatively high coefficient of friction with respect to the carbon seal, and this continues until a break-in phase is completed.
- carbon seal 34 is positioned adjacent to an untreated seal seat 36, and initial operation of this seal assembly results in the break-in phase wherein a coefficient of friction between the surfaces, as shown in FIG. 3 , starts relatively high and gradually decreases.
- FIG. 2 shows seal assembly 22 after the break-in phase.
- a thin transfer film 40 has been transferred from carbon seal 34 to sealing surface 36 of seal seat 32. Once this film 40 is transferred to surface 36, seal assembly 22 operates in steady state conditions for the remainder of life of the seal assembly, and FIG. 3 shows this portion of the operation of seal assembly having a relatively lower coefficient of friction than was present during the break-in phase.
- FIG. 2 shows carbon seal 34 having film controllers 42 which can be provided in carbon seal 34. These film controllers 42 serve to prevent excessive build up of thickness of the transfer film 40, thereby maintaining the desired carbon-carbon sliding surfaces defined by carbon seal 34 on one side and the transfer film 40 on the other.
- FIGS. 4 and 5 together show a seal assembly wherein the seal seat is prepared including at least a sealing surface 36 of the same or similar carbon-based material from which the seal is made.
- sealing surfaces 36, 38 are made of similar carbon-based materials and have a very low coefficient of friction from initial contact through the entire lifetime of the seal assembly.
- a transfer film 44 is still applied over surface 36 of the seal seat.
- this transfer film 44 is of the same material as the seal, and therefore continues to have the desired low coefficient of friction.
- operation begins substantially immediately in a steady state phase, and continues in such steady state phase for the entire lifetime of the seal assembly.
- FIG. 4 shows a block 46 of carbon-based material mounted in the seal seat, for example in a recess or receptacle 48, to coincide with carbon seal 34.
- the entire seal seat could be prepared from this same material.
- a transfer film is still eventually deposited from carbon seal 34 over DLC thin film 44, and the thickness of this transfer film is also controlled, for example by film controllers 42 which can also be present in carbon seal 34 according to this aspect of the disclosure.
- Carbon seal 34 can be provided of a suitable electrocarbon such as FT2650, which is an electrographitic grade carbon.
- the seal seat can typically be provided from the same material. This leads to an initial coefficient of friction, without a break-in phase, of less than 0.1.
- carbon seal 34 can be provided from a carbon-graphite grade such as P-4229, and this could be run against sealing surfaces of the seal seat made from the same material. This results in an initial coefficient of friction, again without break-in phase, of less than 0.12.
- seal 26, 34 can be mounted in a gas turbine engine by being fixed to any suitable structure or seal carrier such as structure 12, 18. Further, seal seat 24, 32 can suitably be mounted to rotational member 10 such that sealing surfaces 28, 30, and 36, 38, respectively, are in close sliding proximity to each other when rotational element 10 is rotated.
- FIGS. 4 and 5 are presented with respect to a rear seal assembly. Illustrations of the same components for a front seal assembly are not provided herein, as the structures would be the same but for being reversed left-to-right.
- seal seat or at least the sealing surface of seal seat, from a similar carbon-based material as that of the seal, in accordance with the present disclosure, produces a low friction and wear-resistant carbon-based seal interface which, for example, can operate effectively between 200°F and 350°F (between 93°C and 177°C), under elevated sliding velocities.
- This in turn, can reduce sub-surface heating (for example due to frictional heating) by reducing the friction co-efficient and improving the break-in phase, which will consequently improve long term wear resistance of the seal system.
- seal assembly as disclosed herein can be useful, for example in bearing seals in gas turbine engines, and in other locations as well, and can significantly increase the endurance life of engine components. Further, utilization of seal assemblies as disclosed herein can significantly reduce overall costs by reducing the number of parts that are stripped prematurely due to wear and thermal damage issues.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Sealing Devices (AREA)
- Mechanical Sealing (AREA)
Abstract
Description
- The disclosure relates to a seal assembly, and more particularly to a bearing seal for a gas turbine engine.
- Gas turbine engines have rotating elements mounted within stationary components at bearings which must be sealed to prevent escape of oil. Such seals are known as bearing seals or oil seals. One form of seal for such purpose is a carbon seal, where a carbon material seal is closely positioned around or relative to a rotating element. When first operated, such a seal results in the transfer of carbon from the carbon seal to the rotating element or seat of the seal assembly to form a film of carbon on the seat. This film is intended to have a low coefficient of friction with the seal, such that escape of oil between the seal and seat is prevented while operating at an acceptably low coefficient of friction.
- This period of operation, when the film is formed, is referred to as the break-in phase of the seal. During break-in, excessive friction can be created, resulting in potential excessive wear on parts of the seal, excessive heat at locations of the seal or seat, and other issues. This issue is all the more serious in seals which are to operate at high velocity and relatively low pressure, which can increase the already high temperature due to friction. The present disclosure addresses this issue.
- In accordance with the present disclosure, there is provided a seal assembly for a gas turbine engine, comprising a seal comprising a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the seal and the seal seat each have a sealing surface which together define a sliding seal, and wherein at least the sealing surface of the seal seat is made of the same carbon material as the sealing surface of the seal.
- In another non-limiting embodiment, the seal seat has a recessed area, and a carbon-based block mounted in the recess, the carbon-based block defining the sealing surface of the seal seat. In still another non-limiting embodiment, the seal seat itself comprises carbon-based material matching the seal.
- In a further non-limiting embodiment, the sealing surfaces of the seal and the seal seat are the same material selected from the group consisting of electrographitic grade carbon, carbon-graphite grade carbon, and combinations thereof.
- In a still further non-limiting embodiment, the sealing surfaces of the seal and the seal seat define a coefficient of friction of less than 0.1.
- Other details of the disclosed seal assembly are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
-
-
FIG. 1 illustrates a simplified cross-sectional view of a portion of a gas turbine engine; -
FIG. 2 illustrates a simplified cross-sectional view of a prior art seal assembly for a gas turbine engine; -
FIG. 3 illustrates coefficient of friction for the seal assembly ofFIG. 2 during break-in and then steady state operation; -
FIG. 4 illustrates a simplified cross-sectional view of a seal assembly for a gas turbine engine as disclosed herein; and -
FIG. 5 illustrates coefficient of friction for the seal ofFIG. 4 with no break-in phase due to the materials of seal and seal seat, and steady state operation. - The disclosure relates to a seal assembly for a gas turbine engine and, more particularly, to a carbon seal assembly for the oil seals of a gas turbine engine.
-
FIG. 1 is a cross-sectional illustration of a portion of a gas turbine engine, and illustrates typical components of such an engine. Of interest to the present disclosure is arotational shaft 10 to which are coupled various operative components of the engine, andstationary structures structure 10 to perform desired functions. Other features of the engine have been removed from the view ofFIG. 1 , or reduced to simple schematic illustration, to allow focus on features which are pertinent to the present disclosure. - In such a setting,
FIG. 1 illustrates afront seal assembly 20 and arear seal assembly 22, each of which serves to prevent leakage or flow of oil past the seal, and thereby maintain oil where desired and needed in the gas turbine engine. -
Seal assembly 20 is defined by afront seal seat 24 and acarbon seal 26.Carbon seal 26 remains stationary relative to rotatingelement 10 andseal seat 24. As shown inFIG. 1 , each of these components has asealing surface surfaces seal assembly 22 is defined by arear seal seat 32 and acarbon seal 34, each of which definessealing surfaces -
FIG. 2 illustrates portions of acarbon seal 34 andseal seat 32, includingsurfaces Seal seat 32 in this known configuration is typically formed of a material such as an Fe-based alloy such as AMS 6490/6491, AMS 6322, or AMS 6323, which may or may not have an additional material applied to it such as a PWA50 material. In any event, the material of the seal seat starts with a relatively high coefficient of friction with respect to the carbon seal, and this continues until a break-in phase is completed. As shown,carbon seal 34 is positioned adjacent to anuntreated seal seat 36, and initial operation of this seal assembly results in the break-in phase wherein a coefficient of friction between the surfaces, as shown inFIG. 3 , starts relatively high and gradually decreases. The image shown in the right hand portion ofFIG. 2 showsseal assembly 22 after the break-in phase. At this stage, athin transfer film 40 has been transferred fromcarbon seal 34 to sealingsurface 36 ofseal seat 32. Once thisfilm 40 is transferred tosurface 36,seal assembly 22 operates in steady state conditions for the remainder of life of the seal assembly, andFIG. 3 shows this portion of the operation of seal assembly having a relatively lower coefficient of friction than was present during the break-in phase. -
FIG. 2 showscarbon seal 34 havingfilm controllers 42 which can be provided incarbon seal 34. Thesefilm controllers 42 serve to prevent excessive build up of thickness of thetransfer film 40, thereby maintaining the desired carbon-carbon sliding surfaces defined bycarbon seal 34 on one side and thetransfer film 40 on the other. -
FIGS. 4 and 5 together show a seal assembly wherein the seal seat is prepared including at least a sealingsurface 36 of the same or similar carbon-based material from which the seal is made. Thus,sealing surfaces surface 36 of the seal seat. However, this transfer film 44 is of the same material as the seal, and therefore continues to have the desired low coefficient of friction. Thus, as shown inFIG. 5 , operation begins substantially immediately in a steady state phase, and continues in such steady state phase for the entire lifetime of the seal assembly. -
FIG. 4 shows ablock 46 of carbon-based material mounted in the seal seat, for example in a recess orreceptacle 48, to coincide withcarbon seal 34. Alternatively, the entire seal seat could be prepared from this same material. Thus, when operation of the seal assembly begins, the coefficient of friction is already low due to the carbon-carbon interaction between the carbon seal and carbon seal seat. Steady state operation of this seal assembly results in a transfer film of carbon material being positioned over the carbon-based seal seat, at least to some extent, and this steady state operation leads to extended useful life of the relevant components. This is shown inFIG. 5 , wherein steady state operation begins substantially immediately, without a significant break-in phase, and the coefficient of friction at steady state is relatively low as compared to that shown inFIG. 3 . During operation of a gas turbine engine having a seal assembly as shown inFIG. 4 , a transfer film is still eventually deposited fromcarbon seal 34 over DLC thin film 44, and the thickness of this transfer film is also controlled, for example byfilm controllers 42 which can also be present incarbon seal 34 according to this aspect of the disclosure. -
Carbon seal 34 can be provided of a suitable electrocarbon such as FT2650, which is an electrographitic grade carbon. The seal seat can typically be provided from the same material. This leads to an initial coefficient of friction, without a break-in phase, of less than 0.1. Alternatively,carbon seal 34 can be provided from a carbon-graphite grade such as P-4229, and this could be run against sealing surfaces of the seal seat made from the same material. This results in an initial coefficient of friction, again without break-in phase, of less than 0.12. - With reference back to
FIG. 1 , it should be appreciated, thatseal structure seal seat rotational member 10 such thatsealing surfaces rotational element 10 is rotated. - It should be appreciated that the illustrations of
FIGS. 4 and 5 are presented with respect to a rear seal assembly. Illustrations of the same components for a front seal assembly are not provided herein, as the structures would be the same but for being reversed left-to-right. - It should be appreciated that preparation of the seal seat, or at least the sealing surface of seal seat, from a similar carbon-based material as that of the seal, in accordance with the present disclosure, produces a low friction and wear-resistant carbon-based seal interface which, for example, can operate effectively between 200°F and 350°F (between 93°C and 177°C), under elevated sliding velocities. This, in turn, can reduce sub-surface heating (for example due to frictional heating) by reducing the friction co-efficient and improving the break-in phase, which will consequently improve long term wear resistance of the seal system.
- Fabricating the seal seat from a carbon-based material to match the seal, as referred to above, creates a carbon-carbon interface with low friction from the beginning of operation, and therefore produces a very short break-in phase. During initial operation, a transferred film is still formed on the seal seat, and this configuration remains through steady state operation of the seal.
- It should be appreciated that the low friction and wear resistance produced by the seal assembly as disclosed herein can be useful, for example in bearing seals in gas turbine engines, and in other locations as well, and can significantly increase the endurance life of engine components. Further, utilization of seal assemblies as disclosed herein can significantly reduce overall costs by reducing the number of parts that are stripped prematurely due to wear and thermal damage issues.
- There has been provided a seal assembly and method wherein the break-in phase is reduced in length and impact on seal components, and wherein steady state performance of the seal assembly is improved as compared to a seal assembly without the initial pre-filming step. While the seal assembly method and article has been described in the context of specific embodiments thereof, other unforeseen alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.
Claims (5)
- A seal assembly (20, 22) for a gas turbine engine, comprising:a seal (26, 34) comprising a carbon material; anda seal seat (24, 32) positioned for rotation relative to the seal (26, 34), wherein the seal (26, 34) and the seal seat (24, 32) each have a sealing surface (28, 30, 36, 38) which together define a sliding seal, and wherein at least the sealing surface (30, 36) of the seal seat (24, 32) is made of the same carbon material as the sealing surface (28, 38) of the seal (26, 34).
- The seal assembly of claim 1, wherein the seal seat (24, 32) has a recessed area (48), and a carbon-based block (46) mounted in the recessed area (48), the carbon-based block (46) defining the sealing surface (30, 36) of the seal seat (24, 32).
- The seal assembly of claim 1 or 2, wherein the seal seat (24, 32) itself comprises carbon-based material matching the seal (26, 34).
- The seal assembly of claim 1, 2 or 3, wherein the sealing surfaces (28, 30, 36, 38) of the seal (26, 34) and the seal seat (24, 32) are the same material selected from the group consisting of electrographitic grade carbon, carbon-graphite grade carbon, and combinations thereof.
- The seal assembly of any preceding claim, wherein the sealing surfaces (28, 30, 36, 38) of the seal (26, 34) and the seal seat (24, 32) define a coefficient of friction of less than 0.1.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201862733598P | 2018-09-19 | 2018-09-19 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3627013A1 true EP3627013A1 (en) | 2020-03-25 |
EP3627013B1 EP3627013B1 (en) | 2023-08-30 |
Family
ID=67998199
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19198453.3A Active EP3627013B1 (en) | 2018-09-19 | 2019-09-19 | Low friction carbon - carbon seal assembly |
Country Status (3)
Country | Link |
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US (1) | US11719114B2 (en) |
EP (1) | EP3627013B1 (en) |
JP (1) | JP2020045902A (en) |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1407413A (en) * | 1972-05-03 | 1975-09-24 | Crane Packing Ltd | Rotary mechanical face seals |
US4336944A (en) * | 1979-08-27 | 1982-06-29 | Raybestos-Manhattan, Inc. | Mechanical-dynamic rotary seal |
EP2662601A1 (en) * | 2011-06-30 | 2013-11-13 | Eagle Industry Co., Ltd. | Shaft seal apparatus |
EP2843270A1 (en) * | 2012-11-02 | 2015-03-04 | Eagle Industry Co., Ltd. | Mechanical seal device |
EP3284980A1 (en) * | 2015-04-16 | 2018-02-21 | Eagle Industry Co., Ltd. | Sliding part |
EP3388719A1 (en) * | 2017-04-10 | 2018-10-17 | Rolls-Royce Corporation | Reduced friction intershaft seal assembly |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1365287A (en) * | 1970-12-11 | 1974-08-29 | Ici Ltd | Graphite compositions |
JPS59117957A (en) | 1982-12-22 | 1984-07-07 | Taiho Kogyo Co Ltd | Mechanical seal |
US5042824A (en) * | 1990-02-08 | 1991-08-27 | Eg&G Sealol, Inc. | Balanced shrink fit seal ring assembly |
DE10135477A1 (en) * | 2001-07-18 | 2003-02-06 | Tea Gmbh | Sliding pairing with a sliding element made on the basis of carbon |
JP2006275286A (en) * | 2005-03-02 | 2006-10-12 | Ebara Corp | Diamond coated bearing or seal structure, and fluid machine with the same |
US7754350B2 (en) * | 2006-05-02 | 2010-07-13 | United Technologies Corporation | Wear-resistant coating |
WO2009107440A1 (en) * | 2008-02-25 | 2009-09-03 | イーグル工業株式会社 | Shaft sealing device |
US20090277197A1 (en) * | 2008-05-01 | 2009-11-12 | Gambiana Dennis S | Evaporator apparatus and method for modulating cooling |
DE102011116162A1 (en) * | 2011-10-14 | 2013-04-18 | Eagleburgmann Germany Gmbh & Co. Kg | Sliding ring of a mechanical seal assembly with run-time-prolonging properties and process for its preparation |
JP6625473B2 (en) * | 2016-03-31 | 2019-12-25 | イーグル工業株式会社 | Sealed structure |
-
2019
- 2019-09-18 US US16/574,586 patent/US11719114B2/en active Active
- 2019-09-19 EP EP19198453.3A patent/EP3627013B1/en active Active
- 2019-09-19 JP JP2019170048A patent/JP2020045902A/en active Pending
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1407413A (en) * | 1972-05-03 | 1975-09-24 | Crane Packing Ltd | Rotary mechanical face seals |
US4336944A (en) * | 1979-08-27 | 1982-06-29 | Raybestos-Manhattan, Inc. | Mechanical-dynamic rotary seal |
EP2662601A1 (en) * | 2011-06-30 | 2013-11-13 | Eagle Industry Co., Ltd. | Shaft seal apparatus |
EP2843270A1 (en) * | 2012-11-02 | 2015-03-04 | Eagle Industry Co., Ltd. | Mechanical seal device |
EP3284980A1 (en) * | 2015-04-16 | 2018-02-21 | Eagle Industry Co., Ltd. | Sliding part |
EP3388719A1 (en) * | 2017-04-10 | 2018-10-17 | Rolls-Royce Corporation | Reduced friction intershaft seal assembly |
Also Published As
Publication number | Publication date |
---|---|
EP3627013B1 (en) | 2023-08-30 |
US11719114B2 (en) | 2023-08-08 |
US20210062665A1 (en) | 2021-03-04 |
JP2020045902A (en) | 2020-03-26 |
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